TASK 72-41-22-200-006-B00 HPC Stage 6 Stator Vane - Examine, Inspection-006

DMC:V2500-A0-72-41-2206-00B-300A-C|Issue No:006.00|Issue Date:2021-08-01

Export Control

EAR Export Classification: Not subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3), except for the following Service Bulletins which are currently published as EAR Export Classification 9E991: SBE70-0992, SBE72-0483, SBE72-0580, SBE72-0588, SBE72-0640, SBE73-0209, SBE80-0024 and SBE80-0025.

Copyright

© IAE International Aero Engines AG (2001, 2014 - 2021) The information contained in this document is the property of © IAE International Aero Engines AG and may not be copied or used for any purpose other than that for which it is supplied without the express written authority of © IAE International Aero Engines AG. (This does not preclude use by engine and aircraft operators for normal instructional, maintenance or overhaul purposes.).

Applicability

All

Common Information

TASK 72-41-22-200-006-B00 HPC Stage 6 Stator Vane - Examine, Inspection-006

Effectivity

FIG/ITEM

PART NO.

01-350

6A4231

01-350

6A7424

01-350

6A7481

01-350

6A8767

01-400

6A4230C01

01-400

6A7423C01

01-400

6A7482C01

01-400

6A8765

01-448

6A4230C01

01-448

6A7423C01

01-448

6A7482C01

01-448

6A8765

01-450

6A4230C02

01-450

6A7423C02

01-450

6A7482C02

01-450

6A8766

General

This TASK gives the procedure for the inspection of the HP compressor stage 6 stator vanes.

Nicks and dents 0.005 in. (0.13 mm) or less are acceptable without limit to the airfoil and gas washed surfaces of the platforms.

Fig/item numbers in parentheses in the procedure agree with those used in the IPC. Only the primary Fig/item numbers are used. For service bulletin variants refer to the IPC.

The policy that is necessary for inspection in SPM TASK 70-20-01-200-501.

All the parts must be cleaned before any part is examined (CLEANING-000).

All the parts must be visually examined for damage, corrosion and wear. Any defects that are not identified in the procedure must be referred to IAE.

The procedure for those parts which must have a crack test is given in Step. Do the crack test before the part is visually examined.

Do not discard any part until you are sure there are no repairs available. Refer to the instructions in repair before a discarded part is used again or oversize parts are installed.

Parts which should be discarded can be held although no repair is available. The repair of a discarded part can be shown to be necessary at a subsequent date.

All the parts must be examined to make sure that all the repairs have been completed satisfactorily.

The practices and processes referred to in the procedure by the TASK/SUBTASK numbers are in SPM.

References

Refer to SPM for data on these items:

Definitions of damage, SPM TASK 70-02-02-350-501,

Inspection of parts, SPM TASK 70-20-01-200-501.

Some data on these items is contained in this TASK. For more details on these items Refer to SPM.

Method of test for crack indicators,

Chemical processes,

Surface protection.

Preliminary Requirements

Pre-Conditions

NONE

Support Equipment

NONE

Consumables, Materials and Expendables

NONE

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-41-22-230-088 Examine the Stage 6 Stator Vanes for Cracks

    1. Clean the parts. Refer to TASK 72-41-22-100-000 (CLEANING-000).

      2. Do the test for cracks on the parts that are given below.

        PART IDENT

        TASK/SUBTASK

        Stage 6 Stator Vanes

        1. Cracked.

          1. Airfoil tips.

          1. Refer to Step.

          2. All remaining areas.

          1. Reject.

    2. SUBTASK 72-41-22-220-184-001 Examine the Stage 6 Stator Vanes Concave and Convex Airfoil Surfaces at Locations 1 and 2, (01-350, 01-400, 01-448 and 01-450, 6A7424, 6A7423C01, 6A7423C01 and 6A7423C02) (Pre SBE 70-0714 and SBE 70-0726)

    1. Refer to Figure, Figure and Figure.

      2. Nicked.

        1. Up to 0.005 in. (0.13 mm) in depth.

        1. Accept.

        2. More than Step.

        1. Repair, VRS6503 TASK 72-41-22-300-024 (REPAIR-024).

      3. Dented.

        1. Up to 0.005 in. (0.13 mm) in depth.

        1. Accept.

        2. More than in Step.

        1. Repair, VRS6503 TASK 72-41-22-300-024 (REPAIR-024).

          NOTE

          A Tallysurf measuring instrument must not be used.

      4. Examine the surface finish of the vanes. Use 10 percent of the vanes that have been removed.

        1. Roughness up to 30 micro-inches (0.80 micrometers).

        1. Accept.

        2. More than in Step.

        1. Repair, VRS6499 TASK 72-41-22-300-025 (REPAIR-025).

    3. SUBTASK 72-41-22-220-184-002 Examine the Stage 6 Stator Vanes Concave and Convex Airfoil Surfaces at Locations 1 and 2 (SBE 70-0714 and SBE 72-0561)

    1. Refer to Figure.

      2. Nicked.

        1. Up to 0.005 in. (0.13 mm) in depth.

        1. Accept.

        2. More than Step.

        1. Repair, VRS6503 TASK 72-41-22-300-024 (REPAIR-024).

      3. Dented.

        1. Up to 0.005 in. (0.13 mm) in depth.

        1. Accept.

        2. More than in Step.

        1. Repair, VRS6503 TASK 72-41-22-300-024 (REPAIR-024).

      4. Surface finish.

        1. Roughness of 10 micro-inches (0.25 micrometers) or less.

        1. Accept.

        2. More than Step.

        1. Repair, VRS6499 TASK 72-41-22-300-025 (REPAIR-025).

    4. SUBTASK 72-41-22-220-185 Examine the Stage 6 Stator Vanes Leading and Trailing Edges at Locations 3 and 4

    1. Refer to Figure, Figure and Figure.

      2. Nicked.

        1. Up to 0.005 in. (0.13 mm) in depth.

        1. Accept.

        2. More than Step.

        1. Repair, VRS6503 TASK 72-41-22-300-024 (REPAIR-024).

      3. Dented.

        1. Up to 0.005 in. (0.13 mm) in depth.

        1. Accept.

        2. More than in Step.

        1. Repair, VRS6503 TASK 72-41-22-300-024 (REPAIR-024).

    5. SUBTASK 72-41-22-220-219 Examine the Stage 6 Stator Vanes Chordal Width (SBE 70-0714. SBE 70-0726, SBE 70-0320 and SBE 72-0561)

    1. SBE 70-0714: Announcement of super polished HP Compressor Blades and Vanes.

    2. SBE 70-0726: Announcement of HP Compressor Blades and Vanes without super polished finish.

    3. SBE 72-0320: Introduction of revised stage 6, 7 and 10 stator vanes with chordal machining of rear platform location features.

    4. SBE 72-0561: Engine - HP Compressor - V2500 SelectOne Production - HP Compressor upgrade.

    5. Refer to Figure.

      6. Minimum chord for Z1 and Z2 at the heights A and B not less than value X.

      1. Accept.

      7. Less than value X.

      1. Reject.

    6. SUBTASK 72-41-22-220-186 Examine the Stage 6 Stator Vanes Faces at Locations 5 and 6

    1. Refer to Figure.

      2. Galled.

        1. Not more than 0.002 in. (0.05 mm) in depth. This must not be more than 25 percent of the touch area.

        1. Accept.

        2. Not more than 0.005 in. (0.13 mm) in depth. This must not be more than 25 percent of the touch area and not less than 0.0787 in. (2.000 mm) from face 7.

        1. Accept.

        3. More than in Step or Step.

        1. Reject.

    7. SUBTASK 72-41-22-220-187 Examine the Stage 6 Stator Vanes Faces at Location 7

    1. Refer to Figure, Figure and Figure.

      2. Galled.

        1. Up to 0.006 in. (0.15 mm) in depth, not less than 0.040 in. (1.00 mm) away from the land face.

        1. Accept.

        2. More than in Step.

        1. Reject.

    8. SUBTASK 72-41-22-220-188 Examine the Stage 6 Stator Vanes Airfoil Tips at Location 1057 for Cracks and Rubs

    1. Refer to Figure, Figure and Figure.

      2. Cracked.

      1. Repair, VRS6490 TASK 72-41-22-300-023 (REPAIR-023) or Repair, VRS9535 TASK 72-41-22-300-026 (REPAIR-026).

      3. Rubbed.

        1. Within limits in TASK 72-41-30-440-002-B01.

        1. Accept.

        2. Identified with radius beyond min value in TASK 72-41-30-440-002-B01.

        1. Repair, VRS6490 TASK 72-41-22-300-023 (REPAIR-023) or Repair, VRS9535 TASK 72-41-22-300-026 (REPAIR-026).

    9. SUBTASK 72-41-22-220-189 Examine the Stage 6 Stator Vanes Cheeks at Locations 8, 9, 10 and 11

    1. Refer to Figure, Figure and Figure.

      2. Galled.

        1. Up to 0.015 in. (0.38 mm) in depth. This must not be in an area more than 50 percent of each surface.

        1. Accept.

        2. More than in Step.

        1. Reject.

    10. SUBTASK 72-41-22-220-190 Examine the Stage 6 Stator Vanes at Location 1120 and Location 1122

    1. Refer to Figure, Figure and Figure.

      2. Location 1120.

        1. If the thickness of the land is between 0.0755 in. to 0.0787 in. (1.92 mm to 2.00 mm).

        1. Accept.

        2. If the thickness of the land is between 0.0680 in. to 0.0755 in. (1.73 mm to 1.92 mm) over an area of not more than 25 percent.

        1. Accept.

        3. If the thickness of the land is between 0.0680 in. to 0.0755 in. (1.73 mm to 1.92 mm) over an area of more than 25 percent.

        1. Reject.

        4. If the thickness of the land is less than the minimum in Step.

        1. Reject.

        5. If less than 10 percent reduction in thickness over an areas of less than 25 percent.

        1. Accept.

        6. More than Step.

        1. Reject.

      3. Location 1122.

        1. If the thickness of the land is between 0.0952 in. to 0.0984 in. (2.42 mm to 2.50 mm).

        1. Accept.

        2. If the thickness of the land is between 0.0856 in. to 0.0952 in. (2.18 mm to 2.42 mm) over an area of not more than 25 percent.

        1. Accept.

        3. If the thickness of the land is between 0.0856 in. to 0.0952 in. (2.18 mm to 2.42 mm) over an area of more than 25 percent.

        1. Reject.

        4. If the thickness of the land is less than the minimum Step.

        1. Reject.

        5. If less than 10 percent reduction in thickness over an areas of less than 25 percent.

        1. Accept.

        6. More than in Step.

        1. Reject.

    11. SUBTASK 72-41-22-220-213 Examine the Stage 6 Stator Vanes Platform (Annulus Surface) at Location 13 (SBE 70-0714 and SBE 72-0561)

      NOTE

      Class identification marks as scores.

    1. Refer to Figure.

      2. Surface finish.

        1. Roughness of 16 micro-inches (0.40 micrometers) or less.

        1. Accept.

        2. Roughness more than in Step.

        1. Reject.

      3. Scored/Scratched.

        1. More than 0.005 in. (0.13 mm) in depth.

        1. Reject.

        2. Not more than 0.005 in. (0.13 mm) in depth.

        1. Accept.

        3. Airfoil fillet radius.

        1. Reject.

        4. On face edge.

        1. Refer to SPM TASK 70-35-03-300-501 to remove score.

        5. Remaining face.

        1. Accept.

    12. SUBTASK 72-41-22-220-246 Examine the Stage 6 Stator Vanes Platform (Bottom Face)

    1. Refer to Figure and Figure.

      2. Part marking and repair symbol location 14.

        1. On face edge.

        1. Refer to SPM TASK 70-35-03-300-501 to remove score.

        2. Remaining face.

        1. Accept.

    13. SUBTASK 72-41-22-220-191 Examine the Stage 6 Stator Vanes All Remaining Surfaces

      1. Nicked, dented or scored/scratched.

        1. Up to 0.005 in. (0.13 mm) in depth.

        1. Accept.

        2. More than in Step.

        1. Reject.

    14. Figure: Stage 6 Stator Vanes - Inspection Locations

    Stage 6 Stator Vanes - Inspection Locations

    Figure: Stage 6 Stator Vanes - Inspection Locations

    Stage 6 Stator Vanes - Inspection Locations

    Figure: Stage 6 stator vanes - Inspection locations

    Stage 6 stator vanes - Inspection locations

    Figure: Stage 6 Stator Vanes Chordal Width Locations and Limits

    Stage 6 Stator Vanes Chordal Width Locations and Limits

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Revised the procedural steps. (20VG155)